Aircraft turbojet engine thrust reverser with a lower number of actuators

Abstract

This cascade-type thrust reverser with one-piece moving cowl includes rails able to slide in guideways positioned on each side of a suspension pylon. This thrust reverser includes just two actuators positioned near the rails and able to cause this cowl to slide on the guideways between its direct-jet and reverse-jet positions. It also has means capable of compensating for forces that have a tendency to misalign the rails with respect to the guideways, thus preventing them from jamming in one another.

What is claimed is: 
     
         1 . A cascade-type thrust reverser with a one-piece moving cowl comprising rails able to slide in guideways positioned on either side of a suspension pylon, comprising only two actuators positioned near said rails and able to cause this cowl to slide on said guideways between its direct jet and reverse jet positions, and comprising means capable of compensating for forces that have a tendency to misalign said rails with respect to said guideways, thus preventing them from jamming in one another, wherein said means are selected from at least one of:
 means for compensating the tilting torque of the moving cowl caused by the pressurization of the cold flow tunnel of the reverser, and   thrust reverser flaps of the reverser, arranged so as to exert a thrust force on the upstream edge of the inner wall of said moving cowl.   
     
     
         2 . The reverser according to  claim 1 , wherein said compensating means comprise means for pressurizing the outer wall of said outer cowl. 
     
     
         3 . The reverser according to  claim 2 , wherein said pressurizing means comprise an O-ring arranged upstream from the outer wall of said moving cowl, and an absence of seal upstream from the inner wall of said moving cowl. 
     
     
         4 . The thrust reverser according to  claim 2 , wherein said pressurizing means comprise an O-ring on the inner wall of said moving cowl, associated with a limited leak on the outer wall and at least one expander situated through the inner wall. 
     
     
         5 . A nacelle for a turbojet engine of an aircraft, wherein it comprises a thrust reverser according to  claim 1 .